This SAE Standard establishes the requirements for lubricating oils containing ashless dispersant additives to be used in four-stroke cycle, reciprocating piston aircraft engines. This document covers the same lubricating oil requirements as the former military specification MIL-L-22851. Users should consult their airframe or engine manufacturers manuals for the latest listing of acceptable lubricants.

E-38 Aviation Piston Engine Fuels and Lubricants

Lubricating Oils, Aircraft Piston Engine (Non-Dispersant Mineral Oil)

J1966_202010 (Current)

10/28/2020

E-38 Aviation Piston Engine Fuels and Lubricants

Lubricating Oil, Aircraft Piston Engine (Ashless Dispersant)

J1899_202010-TEST-REC (Historical)10/28/2020

E-38 Aviation Piston Engine Fuels and Lubricants

Measurement of the Total Ash Content of Aviation Piston Engine Oils by a Calculation Method

J1787_202009-TEST-REC (Historical)09/29/2020

E-38 Aviation Piston Engine Fuels and Lubricants

Measurement of the Total Ash Content of Aviation Piston Engine Oils by a Calculation Method

J1787_202009 (Current)

09/29/2020

E-38 Aviation Piston Engine Fuels and Lubricants

SMART Solar Sail

TBMG-3720507/01/2020

The SMART (Super Miniaturized Autonomous Reconfigurable Technology) Solar Sail is a deployable, fully autonomous solar sail for use in very fine station-keeping of a spacecraft. The solar sail would be highly deformable from an initially highly compressed configuration, yet also capable of enabling very fine maneuvering of the spacecraft by means of small sail-surface deformations.

Preignition Rating of Spark Plugs

J549_202006 (Current)

06/15/2020

This SAE Recommended Practice describes the equipment and procedures used in obtaining preignition ratings of spark plugs.

Ignition Standards Committee

Elastomer: Methyl Phenyl Vinyl Silicone (PVMQ) Very Low Temperature/Aircraft Piston Engine Oil Resistant High Strength/Tear Resistant 45 to 55 Durometer Type ‘A’ Hardness For Products in Aircraft Piston Engine Oil/Low Temperature Environments

AMS3345G-TEST-REC (Historical)05/18/2020

This specification covers a methyl phenyl vinyl silicone rubber material that can be used to manufacture product in the form of sheet, strip, tubing, molded shapes, and extrusions. For molded rings, compression seals, O-ring cord, and molded-in-place gaskets for aeronautical and aerospace applications, use the corresponding AMS7000 series specification.

AMS CE Elastomers Committee

AMS3345G (Current)

05/18/2020

AMS CE Elastomers Committee

Supersonic Spike Diffuser

TBMG-3682405/01/2020

The basic mode of operation for all passive supersonic diffusers is to enable a plume’s inherent power to drive the outer boundary of the exhaust jet to the diffuser wall so that the entire cross-section of the flow has a speed greater than that of sound. This allows mass removal from the area surrounding the nozzle via entrainment. The result is a low-pressure environment similar to the altitude at which the nozzle was designed to operate. Additionally, the nature of supersonic flow prevents pressure interference from the downstream environment.

Numerical Investigation of the Effects of Port Water Injection Timing on Performance and Emissions in a Gasoline Direct Injection Engine

2020-01-028704/14/2020

Port water injection is considered as a promising strategy to further improve the combustion performance of internal combustion engines for its benefit in knock resistance by reducing the cylinder temperature. A thorough investigation of the port water injection technique is required to fully understand its effects on the engine combustion process. This study explores the potential of the port water injection technique in improving the performance of a turbo charged Gasoline Direct Injection engine. A 3D computational fluid dynamics model is applied to simulate the in-cylinder mixing and combustion for this engine both with and without water injection. Different water injection timings are investigated and it is found that the injection timing greatly effects the mass of water which enters the combustion chamber, both in liquid and vapor form. Comparison have been given between the original engine and the water injection one and the results show that the water injection can reduce the

Yin, Peng, Li, Xuesong, Hung, David, Fan, Yadong, Xu, Min

Experimental Analysis of a Multiple Radiator Cooling System with Computer Controlled Flow Rates

2020-01-094404/14/2020

The automotive cooling system configuration has remained fixed for many decades with a large radiator plus fan, coolant pump, and bypass valve. To reduce cooling system power consumption, the introduction of multiple computer-controlled heat exchangers may offer some benefits. A paradigm shift from a single large radiator, sized for maximum load, to n-small radiators with individual flow control valves should allow fine tuning of the heat rejection needs to minimize power. In this project, a series of experimental scenarios featuring two identical parallel radiators have been studied for low thermal load engine cooling (e.g., idling) in ground transportation applications. For high thermal load scenarios using two radiators, the fans required between 1120 - 3600 W to maintain the system about the coolant reference temperature of 85oC. In contrast at reduced thermal loads, a single radiator configuration with half the heat transfer surface area required between 550 - 1000 W for the same

Syed, Zaker, Wagner, John

Influence of Port Water Injection on the Combustion Characteristics and Exhaust Emissions in a Spark-Ignition Direct-Injection Engine

2020-01-029404/14/2020

It is well known that engine downsizing is still the main energy-saving technology for spark-ignition direct-injection (SIDI) engine. However, with the continuous increase of the boosting ratio, the gasoline engine is often accompanied by the occurrence of knocking, which has the drawback to run the engine at retarded combustion phasing. Besides, in order to protect the turbine blades from being sintered by high exhaust temperature, the strategies of fuel enrichment are often taken to reduce the combustion temperature, which ultimately leads to a high level of particulate number emission. Therefore, to address the issues discussed above, the port water injection (PWI) techniques on a 1.2-L turbocharged, three-cylinder, SIDI engine were investigated. Measurements indicate that the optimization of spark timing has a significant impact on its performance. The two factors of the water substance itself and spark advance caused by the knock mitigation are trade-offs, which eventually affect

Fan, Yadong, Wu, Tianbao, Li, Xuesong, Xu, Min, Hung, David

Temperature Measurement, Well Insert Type

ARP175A (Current)

04/14/2020

A-4 Aircraft Instruments Committee

Limiting Creep in Aerospace Materials

TBMG-3661304/01/2020

The Larson-Miller parameter was first used in the 1950s as a model to predict the lifetime of a material vs. time and temperature. Without close attention to materials selection, many products are not fit for purpose due to mechanical stress and natural creep. That’s why creep resistant materials are so important in the aerospace industry.

The impacts of Diesel cycle engines on the operating costs of the Cessna 172 Skyhawk and JT-A aircraft.

2019-36-032101/13/2020

Diesel engines have been used on the aeronautical market for a long time. Despite this fact, there are few studies showing the potential cost savings of using this type of technology. In this way, the goal of this paper is to find out whether or not it is advantageous to use an Otto or Diesel cycle engine on general aviation light aircraft. It is well known that both of them have pros and cons, however, the possibility of using Jet A-1 (kerosene) as fuel gives the Diesel engine a clear advantage in a market like Brazil, where the price of the regular piston fuel (AvGas) keeps rising to astonishing values. Throughout this paper, a detailed study of the fixed and variable costs of two similar aircraft, both Cessnas 172 equipped with Otto and Diesel cycle engines is conducted, comparing fuel consumption, performance levels, and other factors. Even though the latter engine has a higher fixed operating cost, the advantages found in this study makes the Diesel motor a step forward of its

Diniz, Samuel Cunha, Henrique de Assis Coelho, Eduardo, Rodrigues de Oliveira, Gabriel, de Cardoso Oliveira, Lucas, Morais, Samuel Renan Costa, Vasques, Victor Britto, Jorge Machado, Luiz Henrique

Using Engine Test Data to Model Engine Performance

AIR5509A (Current)11/05/2019

This document defines the process steps involved in collecting and processing engine test data for use in understanding engine behavior. It describes the use of an aero-thermal cycle model for reduction and analysis of those data. The analysis process may include the calculation of modifiers to match the model to measured data and prediction of engine performance based on that analysis.

S-15 Gas Turbine Perf Simulation Nomenclature and Interfaces

Aircraft Engine Icing Event Avoidance and Mitigation

TBMG-3473807/01/2019

Innovators at NASA’s Glenn Research Center have developed a new means of avoiding and mitigating icing events for aircraft flying above 14,000 feet, dramatically improving aviation safety and reducing operating costs.

SAE 17.6 Cubic Inch Spark Plug Rating Engine

J2203_201906 (Current)06/11/2019

This SAE Standard defines the standard engine to be used in determining spark plug preignition ratings. The engine is known as the SAE 17.6 Cubic Inch Spark Plug Rating Engine.

Ignition Standards Committee

High Power-Density, High Efficiency, Mechanically Assisted, Turbocharged Direct-Injection Jet-Ignition Engines for Unmanned Aerial Vehicles

01-12-01-000205/02/2019

More than a decade ago, we proposed combined use of direct injection (DI) and jet ignition (JI) to produce high efficiency, high power-density, positive-ignition (PI), lean burn stratified, internal combustion engines (ICEs). Adopting this concept, the latest FIA (Fédération Internationale de l’Automobile) F1 engines, which are electrically assisted, turbocharged, directly injected, jet ignited, gasoline engines and work lean stratified in a highly boosted environment, have delivered peak power fuel conversion efficiencies well above 46%, with specific power densities more than 340 kW/liter. The concept, further evolved, is here presented for unmanned aerial vehicle (UAV) applications. Results of simulations for a new DI JI ICE with rotary valve, being super-turbocharged and having gasoline or methanol as working fuel, show the opportunity to achieve even larger power densities, up to 430 kW/liter, while delivering a near-constant torque and, consequently, a nearly linear power curve

Boretti, Alberto

Computational Optimization of Pressure Wave Reflection on the Piston Surface for Single Point Autoignition Gasoline Engine with Colliding Pulsed Supermulti-Jets Leading to Noiseless-High Compression and Nearly-Complete Air-Insulation

2019-01-023504/02/2019

A new engine concept based on pulsed supermulti-jets colliding at a small area around the chamber center was proposed in our previous research. It was expected to provide noiseless high compression ratio and nearly-complete air-insulation on chamber walls, leading to high thermal efficiency. In the previous reports, three-dimensional computations for the unsteady compressible Navier-Stokes equation were conducted, which were qualitative because of using regular grid method. This time, we develop a new numerical code in order to quantitatively simulate the compression level caused by the jets colliding with pulse. It is achieved by applying a staggered grid method to improve conservatibity of physical quantities at very high compression in combustion phenomena. Computations at a simple condition were fairly agreed with a theoretical value. Computational results obtained for a complex geometry of an engine by the new code had less error than one with previous codes. In addition, the

Hosoi, Aya, Konagaya, Remi, Kawaguchi, Sota, Sogabe, Yasuhiro, Yamashita, Yuya, Naitoh, Ken

Supplemental Propulsion System Performance Station Designation

AIR6508 (Current)01/03/2019

This SAE Aerospace Information Report (AIR) supplements the AS755 performance station designation system for complex or unconventional propulsion cycles and their derivatives. The station numbering conventions presented herein are for use in all communications concerning propulsion system performance such as computer programs, data reduction, design activities, and published documents. They are intended to facilitate calculations by the program user without unduly restricting the method of calculation used by the program supplier. The contents of this document will follow AS755 and AS6502 where applicable. The list of symbols presented herein will be used for identification of input and output parameters. These symbols are not required to be used as internal parameter names within the engine subprogram.

S-15 Gas Turbine Perf Simulation Nomenclature and Interfaces

PROPELLER SHAFT ENDS - FLANGED SMALL AIRCRAFT ENGINE

ARP502A (Current)11/28/2018

E-25 General Standards for Aerospace and Propulsion Systems

Measurement Data and Reference Values for Compounds Potentially Found in Aircraft Engine Bleed Air

AIR7521 (Current)10/09/2018

This document summarizes published measurement data and reference values for marker chemical compounds listed in ARP4418 (see 2.1.1) potentially found in aircraft engine bleed air.

E-31B Bleed Air Committee

Modeling of Ducted-Fan and Motor in an Electric Aircraft and a Preliminary Integrated Design

01-11-02-000710/04/2018

Electric ducted-fans with high power density are widely used in hybrid aircraft, electric aircraft, and VTOL vehicles. For the state-of-the-art electric ducted-fan, motor cooling restricts the power density increase. A motor design model based on the fan hub-to-tip ratio proposed in this article reveals that the thermal coupling effect between fan aerodynamic design and motor cooling design has great potential to increase the power density of the motor in an electric propulsion system. A smaller hub-to-tip ratio is preferred as long as the power balance and cooling balance are satisfied. Parametric study on a current 6 kW electric ducted-fan system shows that the highest motor power density could be increased by 246% based on the current technology. Finally, a preliminary design was obtained and experiments were conducted to prove the feasibility of the model.

Jin, Yuzhi, Qian, Yuping, Zhang, Yangjun, Zhuge, Weilin

Burner Rig Testing of A500® C/SiC

TBMG-3302410/01/2018

There is growing interest in developing, testing, and deploying ceramic-matrix composites (CMCs) into commercial and military aerospace gas turbine engines due to their durability under extreme conditions and weight-savings potential. For military applications, the focus is on the afterburning section of the turbine engine, including the flameholder, augmentor liner, and both the convergent and divergent segments of the exhaust nozzle. These are demanding applications because of the high temperatures and rapid thermal cycles.

Impact of Engine Age and Engine Hardware on Low-Speed Pre-Ignition

2018-01-166309/10/2018

Low-speed pre-ignition (LSPI) is a well-studied phenomenon in boosted, spark ignition engines. The impact of lubricant formulation has received a lot of attention in recent years, yet the impact of engine hardware and engine wear on LSPI is still not fully understood. This paper addresses some of these questions using results from multiple installations of the GM 2.0 L LHU engine platform. In the first part of the study, the effect of engine life on LSPI activity was observed, and it was found that engines were susceptible to variations in LSPI activity during the initial LSPI tests with the activity eventually reaching a “stabilized” level. It was further observed that the LSPI activity generally continued to decline at a steady rate as the engine aged. For engines used in LSPI testing, the life of the engine is often limited as LSPI activity decays with age. This reduction in LSPI activity may correlate to the engine liner wear and it is suggested that the amount of oil transport

Kalaskar, Vickey B., Swarts, Andre, Alger, Terrence

Selected Aerospace Diameter Pitch Combinations of Metric 60° Screw Threads for Nuts and Bolts

AS1337A (Current)

08/23/2018

This Aerospace Standard establishes the preferred diameter-pitch combinations of ISO metric 60° screw threads recommended for use in the aerospace industry for metric module bolts and nuts.

E-25 General Standards for Aerospace and Propulsion Systems